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RU2019103284A - AIRCRAFT WING CONSOLE - Google Patents

AIRCRAFT WING CONSOLE Download PDF

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Publication number
RU2019103284A
RU2019103284A RU2019103284A RU2019103284A RU2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A
Authority
RU
Russia
Prior art keywords
specified
winglet
wing
wing console
console
Prior art date
Application number
RU2019103284A
Other languages
Russian (ru)
Inventor
Ханс-Йорг ПЕЧЕР
Фолкер КАССЕРА
Original Assignee
Зе Эркрафт Перфоманс Компани Гмбх
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Зе Эркрафт Перфоманс Компани Гмбх filed Critical Зе Эркрафт Перфоманс Компани Гмбх
Publication of RU2019103284A publication Critical patent/RU2019103284A/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
    • B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (22)

1. Консоль (2, 3) крыла самолета (1), имеющая1. The console (2, 3) of the aircraft wing (1), having длину (b) консоли крыла от фюзеляжа (7) указанного самолета (1) до наружного конца (15) консоли крылаthe length (b) of the wing console from the fuselage (7) of the specified aircraft (1) to the outer end (15) of the wing console и по меньшей мере два винглета (9–12) на указанном наружном конце (15) консоли крыла, соединенных с указанной консолью (2, 3) крыла,and at least two winglets (9-12) at said outer end (15) of the wing console, connected to said wing console (2, 3), при этом расположенный выше по потоку винглет (9, 11) из указанных винглетов предшествует расположенному ниже по потоку винглету (10, 12) из указанных винглетов в направлении полета указанного самолета (1),while the upstream winglet (9, 11) of the specified winglets precedes the downstream winglet (10, 12) of the specified winglets in the direction of flight of the specified aircraft (1), при этом указанный расположенный выше по потоку винглет (9, 11) создает завихрение на концевой части винглета в дополнение к завихрению на концевой части консоли крыла, создаваемому указанной консолью (2, 3) крыла,wherein said upstream winglet (9, 11) creates a vortex at the tip of the winglet in addition to the vortex at the tip of the wing console created by said wing console (2, 3), при этом указанное завихрение на концевой части винглета и указанное завихрение на концевой части консоли крыла накладываются в плоскости между указанными расположенным выше по потоку и расположенным ниже по потоку винглетами (9–12) и перпендикулярно указанному направлению полета,in this case, the specified vortex at the tip of the winglet and the specified vortex at the tip of the wing console are superimposed in the plane between the indicated upstream and downstream winglets (9-12) and perpendicular to the indicated direction of flight, при этом воздушный поток в указанной плоскости скошен относительно указанного направления полета, иin this case, the air flow in the specified plane is skewed relative to the specified direction of flight, and при этом указанный расположенный ниже по потоку винглет (10, 12) приспособлен для создания подъемной силы, имеющей положительную составляющую (Fxn) тяги, в указанном воздушном потоке.wherein said downstream winglet (10, 12) is adapted to create a lifting force having a positive thrust component (F xn ) in said air flow. 2. Консоль (2, 3) крыла по п. 1, отличающаяся тем, что указанная зависимость указанного угла направления скорости воздуха от указанного расстояния имеет промежуточное максимальное значение (18) на некотором расстоянии от указанного наружного конца (15) консоли крыла и не падает до значений указанного угла направления скорости воздуха, которые ниже 25 % меньшего из указанных максимальных значений (17, 18), предпочтительно также большего из указанных максимальных значений (17, 18), между указанным промежуточным максимальным значением (18) и указанным максимальным значением (17) наружного конца консоли крыла.2. Wing console (2, 3) according to claim 1, characterized in that the specified dependence of the specified angle of the direction of air velocity on the specified distance has an intermediate maximum value (18) at some distance from the specified outer end (15) of the wing console and does not fall to values of the specified angle of the direction of air velocity, which are below 25% of the lower of the specified maximum values (17, 18), preferably also the larger of the specified maximum values (17, 18), between the specified intermediate maximum value (18) and the specified maximum value (17 ) the outer end of the wing console. 3. Консоль (2, 3) крыла по п. 1 или 2, отличающаяся тем, что указанный расположенный выше по потоку винглет (9, 11) имеет длину (b1), составляющую от 3 % до 8 % указанной длины (b) консоли крыла.3. Wing console (2, 3) according to claim 1 or 2, characterized in that said upstream winglet (9, 11) has a length (b1) that ranges from 3% to 8% of said wing length (b) wing. 4. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный выше по потоку винглет (9, 11) имеет относительное удлинение, составляющее от 3 до 7.4. Wing console (2, 3) according to any of the preceding claims, characterized in that said upstream winglet (9, 11) has an aspect ratio of 3 to 7. 5. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет относительное удлинение, составляющее от 3 до 7.5. Wing console (2, 3) according to any of the preceding claims, characterized in that said downstream winglet (10, 12) has an aspect ratio of 3 to 7. 6. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет асимметричный профиль консоли крыла для увеличения указанной составляющей (Fxn) тяги.6. Wing console (2, 3) according to any of the preceding claims, characterized in that said downstream winglet (10, 12) has an asymmetric wing console profile to increase said thrust component (F xn ). 7. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный выше по потоку и указанный расположенный ниже по потоку винглеты (9–12) имеют направленную вверх ориентацию относительно указанной консоли (2, 3) крыла, как видно в указанном направлении полета.7. Wing console (2, 3) according to any of the preceding claims, characterized in that said upstream and downstream winglets (9-12) have an upward orientation relative to said wing console (2, 3), as seen in the indicated direction of flight. 8. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет длину (b2) по размаху, составляющую от 105 % до 180 % длины (b1) по размаху указанного расположенного выше по потоку винглета (9, 11).8. Wing console according to any one of the preceding claims, characterized in that said downstream winglet (10, 12) has a span length (b2) ranging from 105% to 180% of a length (b1) in span of said upstream wing the winglet flow (9, 11). 9. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный скошенный воздушный поток в указанной плоскости имеет зависимость угла направления скорости воздуха относительно указанного направления полета от расстояния от области максимального значения (17) угла направления скорости воздуха на указанном наружном конце (15) консоли крыла вследствие указанных наложенных завихрений, при этом указанная зависимость сохраняет значение, составляющее по меньшей мере 25 % указанного максимального значения угла направления скорости воздуха, вплоть до значения указанного расстояния, составляющего по меньшей мере 5 % указанной длины консоли крыла.9. Wing console according to any of the previous paragraphs, characterized in that the specified oblique air flow in the specified plane has a dependence of the angle of the direction of air speed relative to the specified direction of flight from the distance from the region of maximum value (17) of the angle of the direction of air speed at the specified outer end (15 ) the wing console due to the specified superimposed vortices, while the specified dependence retains a value that is at least 25% of the specified maximum value of the angle of direction of the air velocity, up to the value of the specified distance, which is at least 5% of the specified length of the wing console. 10. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный первый винглет наклонен вверх относительно указанного второго винглета, и указанный второй винглет наклонен вверх относительно указанного третьего винглета, при наличии такового.10. A wing console according to any one of the preceding claims, characterized in that said first winglet is tilted upwardly relative to said second winglet, and said second winglet is tilted upwardly relative to said third winglet, if any. 11. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что содержит третий винглет, расположенный ниже по потоку относительно указанного расположенного ниже по потоку винглета.11. A wing console according to any one of the preceding claims, characterized in that it comprises a third winglet located downstream of said downstream winglet. 12. Консоль крыла по п. 11, отличающаяся тем, что указанный третий винглет приспособлен для создания подъемной силы, имеющей положительную составляющую тяги.12. Wing console according to claim 11, characterized in that said third winglet is adapted to generate a lift having a positive thrust component. 13. Консоль крыла по п. 11 или 12, отличающаяся тем, что указанный третий винглет имеет длину, составляющую от 60 % до 120 % длины указанного расположенного ниже по потоку винглета, который расположен выше по потоку относительно указанного третьего винглета.13. A wing cantilever according to claim 11 or 12, wherein said third winglet has a length of 60% to 120% of the length of said downstream winglet that is located upstream of said third winglet. 14. Самолет (1), содержащий две взаимно противоположные консоли (2, 3) крыла по любому из предыдущих пунктов.14. An airplane (1) containing two mutually opposite wing consoles (2, 3) according to any of the preceding paragraphs. 15. Применение усовершенствованной части, содержащей по меньшей мере два винглета (9–12), для прикрепления к самолету (1) с целью создания консоли (2, 3) крыла по любому из пп. 1–13 или самолета (1) по п. 14. 15. The use of an improved part, containing at least two winglets (9-12), for attachment to the aircraft (1) in order to create a wing console (2, 3) according to any one of paragraphs. 1-13 or aircraft (1) according to clause 14.
RU2019103284A 2016-07-12 2017-07-12 AIRCRAFT WING CONSOLE RU2019103284A (en)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
EP16020266.9A EP3269635A1 (en) 2016-07-12 2016-07-12 Airplane wing
EP16020266.9 2016-07-12
EP16020445.9A EP3269636A1 (en) 2016-07-12 2016-11-11 Airplane wing
EP16020445.9 2016-11-11
PCT/EP2017/025204 WO2018010850A1 (en) 2016-07-12 2017-07-12 Airplane wing

Publications (1)

Publication Number Publication Date
RU2019103284A true RU2019103284A (en) 2020-08-12

Family

ID=56418352

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2019103284A RU2019103284A (en) 2016-07-12 2017-07-12 AIRCRAFT WING CONSOLE

Country Status (12)

Country Link
US (1) US11279469B2 (en)
EP (3) EP3269635A1 (en)
JP (1) JP2019521915A (en)
KR (1) KR20190039707A (en)
CN (1) CN109641650B (en)
AR (1) AR109035A1 (en)
BR (1) BR112019000583A2 (en)
CA (1) CA3030319A1 (en)
ES (1) ES2968805T3 (en)
RU (1) RU2019103284A (en)
TW (1) TW201808726A (en)
WO (1) WO2018010850A1 (en)

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